International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Airfoil Design for Martian Airplane Considering Using Global Optimization Methodology

  • Kanazaki, Masahiro (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Utsuki, Motohiro (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Sato, Takaya (Graduate School of System Design, Tokyo Metropolitan University) ;
  • Matsushima, Kisa (Faculty School of Engineering, The University of Toyama)
  • Received : 2015.06.01
  • Accepted : 2015.10.11
  • Published : 2015.12.30
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Abstract

To design airfoils for novel airplanes, new knowledge of aerodynamics is required. In this study, modified Parametric SECtion (PARSEC) which is a airfoil representation is applied to airfoil design using a multi-objective genetic algorithm to obtain an optimal airfoil for consideration in the development of a Martian airplane. In this study, an airfoil that can obtain a sufficient lift and glide ratio under lower thrust is considered. The objective functions are to maximize maximum lift-to-drag ratio and to maximize the trailing edge thickness. In this way, information on the low Reynolds number airfoil could be extracted efficiently. The optimization results suggest that the airfoil with a sharper thickness at the leading edge and higher camber at the trailing edge is more suitable for a Martian airplane. In addition, several solutions which has thicker trailing edge thickness were found.

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References

  1. H. Sobieczky: Parametric Airfoils and Wings, Notes on Numerical Fluid Mechanics, Vieweg, (1998), pp. 71-88.
  2. Y. Tomoyoshi, M. Kanazaki and K. Matsushima.: Design Performance Investigation of Modified PARSEC Airfoil Representation Using Genetic Algorithm, Eurogen 2011 conference, Capua, Italy, (2011).
  3. J. Ogawa, et al.: Outline of Mars Exploration with Lander-Orbiter Synergy (MELOS), JSASS-2009-4093, (2009), (in Japanese)
  4. T. Nonomura, et al.: Aerodynamic Characteristics of Ishii Airfoil (Re=23,000) using LES, The 43th Aero Numerical Simulation Symposium 2011, JAXA-SP-11-015, (2012), pp.43-48. (in Japanese)
  5. K. Deb, S. Agrawal, A. Pratap, T. and Meyarivan: A Fast Elitist Non-Dominated Sorting Genetic Algorithm for Multi-Objective Optimization : NSGA-II, KanGAL Report No. 200001, (2000), Indian Institute of Technology, Kanpur, India.
  6. E. J. Wegman,: Hyper-dimensional data analysis using parallel coordinates, Journal of American Statistical Association, (1985), pp.664-675.
  7. S. Obayashi and G. P. Guruswamy: Convergence Acceleration of an Aeroelastic Navier-Stokes Solver, AIAA J., 33 (1995), pp. 1134-1141. https://doi.org/10.2514/3.12533